EP2245417B1 - Falt- und ausfahrbare tafel - Google Patents

Falt- und ausfahrbare tafel Download PDF

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Publication number
EP2245417B1
EP2245417B1 EP09714842.3A EP09714842A EP2245417B1 EP 2245417 B1 EP2245417 B1 EP 2245417B1 EP 09714842 A EP09714842 A EP 09714842A EP 2245417 B1 EP2245417 B1 EP 2245417B1
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EP
European Patent Office
Prior art keywords
panel
turning
spring
wing
hinge
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EP09714842.3A
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English (en)
French (fr)
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EP2245417A1 (de
Inventor
Arie Ashkenazi
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Elbit Systems Ltd
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Elbit Systems Ltd
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Priority to PL09714842T priority Critical patent/PL2245417T3/pl
Publication of EP2245417A1 publication Critical patent/EP2245417A1/de
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Publication of EP2245417B1 publication Critical patent/EP2245417B1/de
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins

Definitions

  • the present invention relates to foldable and deployable panels.
  • panels Large protruding panels, in which the thickness-dimension is substantially smaller than the length and width dimensions, are key components in a large variety of technologies and objects where they are referred to as “panels".
  • panel encompasses the terms “air foils”,”plates”, “fins”, “wings” and other surfaces when used in the relevant context.
  • object or “body” in the following text refers to devices to which panels are coupled.
  • Panels can vary in size and shape as well as having various spatial configurations, not necessarily flat in shape. Examples for the use of such elements are solar-panels for satellites, various types of broadcasting and reception antennas and the elevation and stabilization devices used in wings of space ships, rockets and projectiles of various kinds.
  • Panels are so designed as to bestow a relative large footprint to the objects they are part of.
  • the advantages of large footprint-feature in flight may cause disadvantages and difficulties in storing, transporting and deploying of panel-equipped objects.
  • US 4,664,339 (Crossfield ) disclosed a missile appendage deployment mechanism for receipt on the side of a missile or projectile and in a stowed position.
  • the mechanism including a wing or fin which is designed, when deployed, to rotate upwardly from the stowed position into a feathered vertical position into the airstream of the missile.
  • the wing moves upwardly from the horizontal stowed position into the vertical feathered position in a continuous smooth motion.
  • US 4,869,442 disclosed a self-deploying airfoil mounted on the body of a device such as an artillery shell projectile and folded down and forward with respect to the relative airstream.
  • the airfoil is attached to a yoke by a pivot pin.
  • the yoke shaft is pivoted in the body in a manner to allow it to pivot 90 degrees tangentially with respect to the body.
  • the airfoil assembly may be retained by a cover which is removable to deploy the airfoil.
  • the shaft of the yoke is mounted at a small angle to the axis of the body so that the airfoil has an angle of attack relative to the airstream when it pivots tangentially outward.
  • a spring starts the airfoil rotating out into the airstream where drag drives it to the 90 degree position.
  • the yoke is locked in the 90 degree position by a yoke lock pin.
  • the airfoil which is rigidly attached by pins to the pivot pin, cannot begin to rotate about the pivot pin until the yoke has rotated 90 degrees.
  • a flat on the head of the pivot pin rides on the surface of the body preventing rotation in a vertical direction until the 90 degrees of tangential rotation has been completed. Aerodynamic lift acting on the airfoil then rotates it upward to a position about normal to the body axis where it is locked by an airfoil lock pin.
  • US 5,326,049 (Rom et al. ) described a wing, normally folded in an inoperative position and to be unfolded to an operative position when the body is accelerated in the direction of the longitudinal axis of the body.
  • the appendage is pivotally mounted about a first pivot axis extending perpendicularly to the longitudinal axis of the body, and also about a second pivot axis extending parallel to the longitudinal axis of the body.
  • the center of gravity of the appendage is outwardly of the first pivot axis in the folded condition of the appendage such that the acceleration of the body produces a moment pivotting the appendage about the first pivot axis.
  • WO8805898 (Eskam et al. ) disclosed a finned projectile or missile having a housing with a longitudinal axis and several fins hinged thereon which in their deployed position are prestressed by springs in a position perpendicular to the longitudinal axis.
  • each fin has at its base an articulated pin inclined towards the longitudinal axis of the fin and is rotatably secured in a bore of the housing so as not to fall off, the bore being matchingly inclined towards the radial plane of the housing.
  • a cavity allowing the pivoting deployment of a corresponding fin is arranged, limited by a stopping shoulder for the fin which maintains said fin in a perpendicular position with respect to the longitudinal axis.
  • EP 1628112 discloses a foldable deployable panel according to the preamble of claim 1.
  • a panel pivotally attached to the body by a first pivot element at a first pivot position and a second pivot element at a second pivot position, wherein the first pivot element is disengageable from the first pivot position, when the panel is aligned in a predetermined orientation, and wherein the second pivot element is fixed at the second pivot position, when the first pivot element is engaged at the first pivot position, and wherein the panel is urged by an energy storing element, when the first pivot element is disengaged from the first pivot position, to move into a deployed position.
  • the energized element comprises a spring.
  • the spring is connected at one end to the second pivot element and at another end to the body.
  • the second pivot element fits into a matching bore when engaged in the second pivot position.
  • the matching bore is provided in a support member comprising two plates in between which a portion of the panel is located when in the deployed state.
  • a support member is provided for supporting the panel in the deployed state.
  • the support member comprises two substantially parallel plates projecting from the body, confining a proximal portion of the panel.
  • the support plates comprise inclined top edges.
  • the panel is selected from a group of panels including: a wing, a solar panel, an antenna.
  • the device is further provided with a fastener for fastening the panel to the body.
  • the fastener is provided with a release mechanism.
  • the release mechanism is selected from a group of release mechanisms including: time-dependent mechanism, remote-controlled mechanism, time-delay mechanism.
  • the device further comprises a locking mechanism for locking the panel in a deployed state.
  • the locking mechanism comprises a snap-lock.
  • a projectile or flying object comprising:
  • each panel pivotally attached to the body by a first pivot element at a first pivot position and a second pivot element at a second pivot position, wherein the first pivot element is disengageable from the first pivot position, when the panel is aligned in a predetermined orientation, and wherein the second pivot element is fixed at the second pivot position, when the first pivot element is engaged at the first pivot position, and wherein the panel is urged by an energy storing element, when the first pivot element is disengaged from the first pivot position, to move into a deployed position.
  • the object is provided with a container for storing the object when the panels are in a folded storing state.
  • the panel in this example is a wing of a projectile.
  • the present invention is not limited to wings and other panels, for example, solar panels, antennas, are also covered by the scope of the present invention as it is defined by the appended claims and their equivalents.
  • Fig. 1 is an illustration of a foldable deployable wing in accordance with an embodiment of the present invention with the wing locked in a deployed position.
  • Fig. 2 is an illustration of the foldable deployable wing shown in fig. 1 with the wing unlocked and turned so as to align with the adjacent body.
  • Fig. 3 is an illustration of the foldable deployable wing shown in Fig. 1 and Fig. 2 with the wing pulled towards the docking pin of an auxiliary flap and turned towards the adjacent body.
  • Fig. 4 is a lateral cross-section illustration of the foldable deployable wing illustrated in Fig. 3 .
  • Fig. 5 is a lateral cross-section illustration of the foldable deployable wing illustrated in Fig. 1 .
  • Fig 6 is a cross-section illustration of a projectile with four foldable deployable wings in accordance with an embodiment of the present invention, in a storing position.
  • Another object of the present invention is to provide a foldable deployable panel, which can be folded neatly and stored in a confined space comparable in its size to the main body to which the panel is attached, thus reducing substantially storage footprint required for main-body having the wing attached.
  • the present invention improves the efficiency of compaction and reduction of packaging volume required for reversibly foldable and deployable panels.
  • the folding of the panel is done by two consecutive turns that bring the panel to a "wrapping" posture along side the object to which it is coupled, where the broad surface of the panel is substantially tangential to the external surface of the object body (i.e., a "folded position").
  • the deployment of the panel is done by implementing the above two consecutive turns in reverse, bringing the panel to a posture erect with respect to the object panel (i.e., a "deployed position").
  • a pyrotechnical-mechanism or some other triggering mechanism commences the deployment of a panel device in accordance with the present invention.
  • the triggering command releases a locking mechanism.
  • the released panel undergoes a first turning about a first turning axis substantially parallel to the surface of the object body, so as to be positioned perpendicularly to the object body in a "first erect posture".
  • the panel is then displaced along the first turning axis to be positioned in a "second erect posture”.
  • a first pivot constrains the motion of the panel to the first turning, except for when the panel is displaced into the second erect posture.
  • the panel undergoes a second turning about a second turning axis that is substantially 90 degrees in perpendicular to the first turning axis, and the panel is inserted into a stabilizing slot between two protective plates, where it is now in the deployed position.
  • a second pivot constrains the motion of the panel to the second turning, except for when the panel is in the first erect posture.
  • the panel can now be locked in place in either a permanent locking arrangement or a locking arrangement that permits the refolding of the panel.
  • the panels are wings of a projectile or other flying object.
  • Wings serve as aerodynamic surfaces providing lift to a flying object.
  • To be effective wings typically span a substantial distance from the body of projectile thus bestowing a large footprint.
  • the footprint dictates large packaging, storage and maintenance volumes.
  • Foldable wings were introduced, and can be seen, for example on aircraft parked on aircraft carrier decks. The need for parking room is met by reducing the wing span of parked aircraft on board aircraft carriers. But when a substantial portion of the wing folded to an up-right position, the space freed on the sides of the aircraft is replaced with occupied space over the aircraft, a space which on the upper deck of an aircraft carrier is abundant. If a winged object is to be stored in on a confined space the wing span may pose a true problem.
  • the present invention introduces a wing of a projectile which can be folded in a twin-action sequence.
  • a first action brings the elongated aspect of the wing to a substantially parallel position along the adjacent body to which it is attached, to a side-by-side configuration with the body, and a second action in which the now side-by-side wing is turned about an axis parallel to the adjacent body, bringing the broad surface of the wing to a tangential stored position with respect to the body external surface.
  • a wing is disclosed that can be easily and swiftly deployed from the folded state and remain fixed in the deployed position.
  • projectile is meant, for the purpose of the present invention and throughout this specification (unless specifically stated otherwise) any object that is ejected, thrown, tossed, propelled, shot, dropped, flown or otherwise dispatched to make its way in air, be it aerodynamically, free falling or any other way of travel in air.
  • the body with the folded wing is stored in a container which holds the folded wing to the body of the object.
  • the folded wing is fastened to the body of the object by a fastener and a controlled release mechanism removes the fastener to allow immediate deployment of the wing.
  • Fig. 1 is an illustration of a foldable deployable wing 12 in accordance an embodiment of the present invention with the wing locked in a deployed position by a flexible snap-lock mechanism 14 in a substantially vertical, perpendicular deployed position, relative to the outer surface of projectile 16.
  • Fig.1 should be viewed in conjunction with Fig. 5 which illustrates a lateral cross-section illustration across the wing folding and deploying device in accordance an embodiment of the present invention with wing 12 in a deployed position. Shown in Fig.1 is snap-lock 14 snapped into gap 18 in wing 12 in a region close to the surface of the projectile 16, in a flight configuration.
  • Two parallel support plates, 20 and 22 (only 20 is visible in Fig. 1 , both shown in Fig.
  • Support plates 20, 22, serve as reinforcement members while snap-lock 14 and spring 28, elastically hold the wing down.
  • Spring 28 rests on stand 26 which is a plate located in between support plates 20 and is secured at one end to pin 30 that runs substantially parallel to the plates, and at the other end to anchoring point 32 which is connected to wing 12.
  • a pin 29 is connected to the end of spring 28, and is coupled to anchoring point 32. Pin 29 serves as a pivot when spring 28 is stretched and wing 12 is pulled from between support plates 20 and 22 (shown in Fig. 2 and explained hereinafter).
  • Fig. 2 is an illustration of the foldable deployable wing shown in fig. 1 with the wing unlocked and turned so as to align with the adjacent body 16.
  • wing 12 is unlocked from the snap-lock 14 and rotated sideway in the direction-of-flight of the projectile utilizing peg 34 as a pivot, bringing it to a side-by-side alignment with the adjacent object 16.
  • the wing is pulled to bring its distal edge 38 towards auxiliary flap 36 so that docking pin 40, extending from the auxiliary flap is inserted and fixed in corresponding bore 42, defining a hinge.
  • With the pulling of the wing spring 28 is stretched and pin 29 at the end of the spring serves as a pivot.
  • the wing pulled from between the support plates 20 and 22 the wing is free to turn side way on the defined hinge between docking pin 40 and pin 29..
  • Fig. 3 is an illustration of wing 12 turned towards the body of projectile 16 on the hinge explained in Fig. 2 .
  • the inclined edge 21 of support plate 22 (one of the two support plates) has a protrusion 22A, distanced from the body of the projectile.
  • Protrusion 22A illustrated in a lateral cross-section illustration in Fig. 4 and Fig. 5 , limits the angular movement of wing 12 to a single, predetermined, folding side towards the body of the projectile when removed from between support plates 20 and 22 and stops the wing from damaging the body of the projectile 16 when folded (prevents "over folding".
  • Fig. 4 is a lateral cross-section illustration of the foldable deployable wing 1 illustrated in Fig. 3 , showing the wing in a folded state, stretched out of the support of support plates 20 and 22. Note that a portion of wing 12 adjacent the body 16 is thinner than the rest of the wing so as to fit that portion of the wing within the support plates 20 and 22, while presenting a substantially aligned outer surface of the support plates and the rest of the wing.
  • Fig. 5 is a lateral cross-section illustration of the foldable deployable panel illustrated in Fig. 1 showing the wing in a deployed (erect) state.
  • Fig 6 is a cross-section illustration of a projectile 16 with four foldable deployable wings 12 in accordance with an embodiment of the present invention, in a storing position within a designated container 50.
  • the container is designed to hold the projectile with its folded wings neatly, keeping the wings in the folded position.
  • the deployment of the wings is simple and swift. When the folded wings are not restrained they can be manually handled to return to the deployed state (as shown in Fig. 1 ).
  • the wings can assume the deployed position simply by removing the restraint that holds the wings in their folded position.
  • the figures ought to be considered in reversed order ( Fig. 3 , then Fig. 2 and then Fig. 1 ).
  • a springs mechanism 28 stores the energy needed (until it hits its stopper, designated 22A in Fig 1 and Fig. 2 ) for the torque needed for convenient deployment of the wings.
  • the first turn which turns the wing along the projectile main body with respect to hinges, uses the spring as a torsion-spring device.
  • the second turn which turns the wing to extend from the projectile main body uses the same spring as a tension-spring, exerting torque on the wing with respect to hinge 34.
  • the displacement of the wing along the first turning axis from the first erect posture to the second erect posture uses the same spring as a tension spring.
  • the projectile with the folded wings is provided with a removable fastener, holding the wings in their folded state. When the fastener is removed or released the wings deploy.
  • Such a fastener may include a time dependent release mechanism or other automatic or remote-controlled release mechanism to ensure proper and timely deployment of the wings.
  • panels of devices such as, but not limited to, sun-energy collectors and various broadcasting and reception antennas are folded and deployed in a manner that was previously described for wings of projectiles but instead of having a spring mechanism (designated 28 in Fig. 1 and Fig. 2 ) that have a default state that favors sliding of a wing (No.12 In Fig. 1 ) back into the confinement of support plates (designated 20 and 22 in Fig. 4 and Fig. 5 ) another "energy-storing" element such as a hydraulic or pneumatic mechanism slides a panel back into the confinement of support plates.
  • panels are folded and deployed in a manner that was previously described for wings of projectiles but instead of having an auxiliary flap (Numbered 36 in Fig. 1 and Fig.2 ) a plate or bar has a pin (designated 40 in the Figures) that inserts into a corresponding bore (No. 42 in the Figures) in the deployed panel.
  • a panel is coupled in a position substantially parallel along the adjacent body to which it is attached, to a side-by-side configuration with the body (as illustrated in Fig. 2 ).
  • the folding and deployment of the panel is done by turning of the panel about an axis parallel to the adjacent body, bringing the broad surface of the panel to a tangential stored position with respect to the body external surface (illustrated in Fig. 3 ).

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerials With Secondary Devices (AREA)

Claims (15)

  1. Falt- und ausfahrbare Plattenvorrichtung, die an einem Korpus eines Gegenstands (16) befestigt ist, wobei die Vorrichtung Folgendes umfasst:
    eine Platte (12), die aus einer Stellung, in der der Korpus mit der breiten Oberfläche der Platte im Wesentlichen tangential zu der Außenfläche des Korpus gewickelt ist, wenn sich die Platte in einer gefalteten Position befindet, in eine Stellung aufrecht in Bezug zu dem Korpus ausgefahren werden kann, wenn sich die Platte in einer ausgefahrenen Position befindet;
    ein erstes Gelenk (40, 42, 29), das an einer ersten Schwenkposition tätig ist, um die Bewegung der Platte (12) auf eine erste Drehung um eine erste Drehachse im Wesentlichen parallel zu der Oberfläche des Korpus (16) aus der gefalteten Position in eine erste aufrechte Stellung in Bezug zu dem Korpus (16) zu beschränken, dadurch gekennzeichnet, dass das erste Gelenk (40, 42, 29) aus der ersten Schwenkposition ausgeklinkt werden kann, wenn die Platte (12) entlang der ersten Drehachse in eine zweite Schwenkposition an einer zweiten aufrechten Stellung verschoben wird;
    wobei die Vorrichtung weiter ein zweites Gelenk (34) umfasst, das an der zweiten Schwenkposition tätig ist, um die Bewegung der Platte (12) auf eine zweite Drehung um eine zweite Drehachse im Wesentlichen senkrecht zu der ersten Drehachse aus der zweiten aufrechten Stellung in die ausgefahrene Stellung zu beschränken, wobei das zweite Gelenk (34) untätig ist, wenn das erste Gelenk (40, 42, 29) in der ersten Schwenkposition eingeklinkt ist, um so Drehbewegung der Platte (12) um die zweite Drehachse zu verhindern; und
    die Vorrichtung weiter ein Energiespeicherelement (28) umfasst, das in der gefalteten Position erregt wird, wobei das Energiespeicherelement (28) tätig ist, um Drehen der Platte (12) um die erste Drehachse aus der gefalteten Position in die erste aufrechte Stellung, Bewegen derselben entlang der ersten Drehachse aus der ersten aufrechten Stellung in die zweite aufrechte Stellung, und Drehen derselben um die zweite Drehachse aus der zweiten aufrechten Stellung in die ausgefahrene Stellung zu erzwingen, wenn das erste Gelenk (40, 42, 29) aus der ersten Schwenkposition ausgeklinkt wird.
  2. Vorrichtung nach Anspruch 1, bei der das Energiespeicherelement eine Feder (28) umfasst.
  3. Vorrichtung nach Anspruch 2, bei der die Feder (28) eine Feder ausgewählt aus der Gruppe von Federn umfasst, die Folgendes einschließt:
    (a) eine Torsionsfeder, die tätig ist, um Ausführen der ersten Drehung durch die Platte (12) zu erzwingen;
    (b) eine Spannfeder, die tätig ist, um die Platte (12) entlang der erste Drehachse aus der ersten aufrechten Stellung in die zweite aufrechte Stellung zu ziehen;
    (c) eine Spannfeder, die tätig ist, um Ausführen der zweiten Drehung durch die Platte (12) zu erzwingen;
    (d) eine Spannfeder, die tätig ist, um die Platte in der ausgefahrenen Position zu halten; und
    (e) eine einzelne Feder, die tätig ist, um das zum Betätigen einer jeglichen Kombination aus den Federn (a), (b), (c) und (d) erforderliche Drehmoment bereitzustellen.
  4. Vorrichtung nach Anspruch 2, bei der das erste Gelenk (40, 42, 49) Folgendes umfasst:
    einen Stift (29), der mit dem Ende der Feder (28) verbunden und an die Platte (12) gekoppelt ist; und
    einen Ankoppelstift (40), der sich von dem Korpus (16) erstreckt, wobei der Ankoppelstift in eine entsprechende Bohrung (42) in der Platte (12) eingesetzt werden kann.
  5. Vorrichtung nach Anspruch 4, bei der der Stift (29) schwenkbar an einen Ankerpunkt (32) in der Platte (12) gekoppelt ist, wobei die Feder eine Spannfeder zum Erzwingen der zweiten Drehung der Platte (12) ist, wobei der Stift (29) während der zweiten Drehung um den Ankerpunkt (32) rotiert.
  6. Vorrichtung nach Anspruch 1, die weiter ein Abstützelement umfasst, welches zum Sichern der Platte (12) in der ausgefahrenen Position vorgesehen ist.
  7. Vorrichtung nach Anspruch 6, bei der das zweite Gelenk (34) Folgendes umfasst: einen aus der Platte (12) vorstehenden Zapfen (34), wobei der Zapfen (34) in eine passende Bohrung an der Kante des Abstützelements eingesetzt werden kann, wenn die Platte (12) sich in der zweiten aufrechten Stellung oder der ausgefahrenen Position befindet.
  8. Vorrichtung nach einem der Ansprüche 6 bis 7, bei der das Abstützelement zwei Platten (20, 22) umfasst, zwischen denen ein Teil der Platte (12) angeordnet ist, wenn sich diese in der ausgefahrenen Position befindet.
  9. Vorrichtung nach Anspruch 8, bei der die Abstützplatten (20, 22) geneigte Oberkanten umfassen.
  10. Vorrichtung nach einem der Ansprüche 8 bis 9, bei der ein Vorsprung (22A) auf einer der Abstützplatten (22) zum Begrenzen von Bewegung der Platte (12) zum Verhindern vorgesehen ist, dass die Platte (12) die Abstützplatten (20, 22) überquert.
  11. Vorrichtung nach einem der vorhergehenden Ansprüche, bei der die Platte (12) aus einer Gruppe von Platten ausgewählt ist, die Folgendes einschließt: einen Flügel, ein Solarmodul, eine Antenne.
  12. Vorrichtung nach einem der vorhergehenden Ansprüche, die weiter mit einer Befestigungseinrichtung zum Befestigen der Platte (12) an dem Korpus (16) versehen ist, wobei die Befestigungseinrichtung mit einem Freigabemechanismus versehen ist, wobei der Freigabemechanismus aus einer Gruppe von Freigabemechanismen ausgewählt ist, die Folgendes umfasst: einen zeitabhängigen Mechanismus, ferngesteuerten Mechanismus, Zeitverzögerungsmechanismus.
  13. Vorrichtung nach einem der vorhergehenden Ansprüche, die weiter einen Verriegelungsmechanismus zum Verriegeln der Platte (12) in einem ausgefahrenen Zustand umfasst.
  14. Projektil oder Flugobjekt, das einen Korpus (16) umfasst, dadurch gekennzeichnet, dass der Korpus eine Mehrzahl von Platten (12) nach einem der vorhergehenden Ansprüche umfasst.
  15. Projektil oder Flugobjekt nach Anspruch 14, das mit einem Behälter zum Lagern des Projektils oder Flugobjekts versehen ist, wenn die Mehrzahl von Platten (12) sich in der gefalteten Position befindet.
EP09714842.3A 2008-02-26 2009-02-23 Falt- und ausfahrbare tafel Active EP2245417B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09714842T PL2245417T3 (pl) 2008-02-26 2009-02-23 Panel nadający się do składania i rozstawiania

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IL189785A IL189785A (en) 2008-02-26 2008-02-26 Foldable and layout board
PCT/IL2009/000204 WO2009107126A1 (en) 2008-02-26 2009-02-23 Foldable and deployable panel

Publications (2)

Publication Number Publication Date
EP2245417A1 EP2245417A1 (de) 2010-11-03
EP2245417B1 true EP2245417B1 (de) 2014-01-01

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US (2) US8378278B2 (de)
EP (1) EP2245417B1 (de)
IL (1) IL189785A (de)
PL (1) PL2245417T3 (de)
WO (1) WO2009107126A1 (de)

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FR3041744B1 (fr) * 2015-09-29 2018-08-17 Nexter Munitions Projectile d'artillerie ayant une phase pilotee.
DE102015014368A1 (de) 2015-11-06 2017-05-11 Mbda Deutschland Gmbh Klappflügel für einen Flugkörper sowie einen Flugkörper mit mindestens einem daran angeordneten Klappflügel
DE102015014367B4 (de) 2015-11-06 2020-07-16 Mbda Deutschland Gmbh Klappflügel für einen Flugkörper und Flugkörper mit mindestens einem daran angeordneten Klappflügel
CN109631682B (zh) * 2019-02-22 2024-01-19 西北工业大学 一种考虑副翼驱动的弹翼单轴旋转展开系统以及展开方法
US11592272B2 (en) * 2021-01-26 2023-02-28 Raytheon Company Aero-assisted missile fin or wing deployment system
CN118025520B (zh) * 2024-04-12 2024-07-26 成都纵横大鹏无人机科技有限公司 机翼折叠机构及无人机

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US8324545B2 (en) 2012-12-04
WO2009107126A1 (en) 2009-09-03
US20100314488A1 (en) 2010-12-16
IL189785A (en) 2013-07-31
PL2245417T3 (pl) 2014-03-31
EP2245417A1 (de) 2010-11-03
IL189785A0 (en) 2009-05-04
US20120036779A1 (en) 2012-02-16
US8378278B2 (en) 2013-02-19

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